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International Journal of Energetic Materials and Chemical Propulsion

Erscheint 6 Ausgaben pro Jahr

ISSN Druckformat: 2150-766X

ISSN Online: 2150-7678

The Impact Factor measures the average number of citations received in a particular year by papers published in the journal during the two preceding years. 2017 Journal Citation Reports (Clarivate Analytics, 2018) IF: 0.7 To calculate the five year Impact Factor, citations are counted in 2017 to the previous five years and divided by the source items published in the previous five years. 2017 Journal Citation Reports (Clarivate Analytics, 2018) 5-Year IF: 0.7 The Immediacy Index is the average number of times an article is cited in the year it is published. The journal Immediacy Index indicates how quickly articles in a journal are cited. Immediacy Index: 0.1 The Eigenfactor score, developed by Jevin West and Carl Bergstrom at the University of Washington, is a rating of the total importance of a scientific journal. Journals are rated according to the number of incoming citations, with citations from highly ranked journals weighted to make a larger contribution to the eigenfactor than those from poorly ranked journals. Eigenfactor: 0.00016 The Journal Citation Indicator (JCI) is a single measurement of the field-normalized citation impact of journals in the Web of Science Core Collection across disciplines. The key words here are that the metric is normalized and cross-disciplinary. JCI: 0.18 SJR: 0.313 SNIP: 0.6 CiteScore™:: 1.6 H-Index: 16

Indexed in

MICRO SOLID PROPELLANT THRUSTER FOR SMALL SATELLITE

Volumen 8, Ausgabe 4, 2009, pp. 321-327
DOI: 10.1615/IntJEnergeticMaterialsChemProp.v8.i4.50
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ABSTRAKT

A micro solid propellant thruster for simple attitude control of a 10 kg class small spacecraft is currently under development. The prototype has ∅ 0.8 mm micro rocket elements, arrayed at a pitch of 1.2 mm on a 22 × 22 mm substance. Initially, solid propellants were used, obtaining only 20% ignition probability with a very long ignition delay (e.g. 1000 ms) as well as very high ignition energy. While observing the tested prototype sample, it became apparent that the main cause of these problems was a gap between the solid propellants and ignition heater. So, the thruster system was improved so that the propellants adhered to the heater. In addition, an ignition charge was used that starts to burn at 210°C, which was acetone having the form of slurry. As a result, a better ignition probability of over 80% in vacuum and half thrust of expectation were gained.

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